# @A300-600 SERVICE BULLETIN REVISION TRANSMITTAL SHEET AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F Fax : (33) 5 61 93 42 51



# MANDATORYMANDATORYMANDATORY
ATA SYSTEM: 57 

### TITLE: WINGS- FLAP BEAM 2 - INSPECTION OF FLAP BEAM BASE AND SIDE MEMBERS. MODIFICATION No.: None This page transmits Revision No.06 of Service Bulletin No.A300-57-6005 ADDITIONAL WORK **CONF ALL No additional work is required by this revision for aircraft modified by any previous issue. REASON Revision No. 06 issued to: - update the effectivity - clarify aircraft not affected by this Service Bulletin - add accomplishment instruction notes in the inspection tasks. CHANGES SUMMARY EFFECTIVITY OPERATOR LIST UPDATED R Fig. A-USAAA FIGURE SOLUTION UPDATED R PLANNING INFORMATION EFFECTIVITY Effectivity has been updated R Configuration definition CONF 001 CONFIGURATION DEFINITION UPDATED R REASON REASON UPDATED R COMPLIANCE Accomplishment Timescale ACCOMPLISHMENT TIMESCALE UPDATED R ACCOMPLISHMENT INSTRUCTIONS TASK 576005- 832-895-001-INSPECTION Accomplishment instructions Notes added R
DATE: Aug 18/86 SERVICE BULLETIN No.: A300-57-6005 REVISION No.: 06 - Nov 14/13 Page: 1 7

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# @A300-600 SERVICE BULLETIN REVISION TRANSMITTAL SHEET
Subtask 576005-910-401-001 SUBTASK SOLUTION UPDATED R Fig. A-UBAAA FIGURE SOLUTION UPDATED R Fig. A-UCAAA FIGURE SOLUTION UPDATED R Fig. A-UDAAA FIGURE SOLUTION UPDATED R Fig. A-UEAAA FIGURE SOLUTION UPDATED R Fig. A-UFAAA FIGURE SOLUTION UPDATED R FILLING INSTRUCTIONS This Service Bulletin has been generated electronically and is reissued as a complete document. Replace the complete document. Put this Revision Transmittal Sheet in front of the Service Bulletin. HISTORY OF PREVIOUS REVISIONS Revision 01 was issued to incorporate rewrites of Paras. 1 and 3 and amendments to references to various manuals. Revision 02 was issued to incorporate changes to the effectivity and changes to Paras. 1.B., 1.C. and inclusion of the Summary pages. Revision 03 was issued to incorporate Change Notices 2A through 2C, and include editorial changes and updates to the effectivity. Revision 04 issued to update the effectivity, to add new aircraft model C4-605R/F and the aircraft MSN 0755 and 0758. Also the statements for the approval and manpower are amended. Revision No. 05 issued to re-introduce an inspection for aircraft Post Modification No. 05815H00968 and aircraft Post Modification No. 11133H05409. Service Bulletin No. A300-57-6006 (Mod. No. 05815H00968). For some aircraft this increases the inspection threshold, for other aircraft it cancels the requirements of this Inspection Service Bulletin (ISB) depending on the aircraft configuration or modification embodiment point. The inspection thresholds and intervals relating to the embodiment of Modification No. 05815H00968 and Modification No. 11133H05409 are now included in the paragraph 1.E (2). REVISION SEQUENCE ORIGINAL: Aug 18/86 REVISION No. : 01 - Feb 26/93 REVISION No. : 02 - Dec 01/93 REVISION No. : 03 - Nov 25/97 REVISION No. : 04 - Oct 25/99 REVISION No. : 05 - Apr 25/13
DATE: Aug 18/86 SERVICE BULLETIN No.: A300-57-6005 REVISION No.: 06 - Nov 14/13 Page: 2 7

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# @A300-600 SERVICE BULLETIN REVISION TRANSMITTAL SHEET REVISION No. : 06 - Nov 14/13

DATE: Aug 18/86 SERVICE BULLETIN No.: A300-57-6005 REVISION No.: 06 - Nov 14/13 Page: 3 7

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# @A300-600 SERVICE BULLETIN REVISION TRANSMITTAL SHEET

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# @A300-600 SERVICE BULLETIN SUMMARY AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F Fax : (33) 5 61 93 42 51 This summary is for information only and is not approved for modification of the aircraft. 

# MANDATORYMANDATORYMANDATORY
ATA SYSTEM: 57 

### TITLE: WINGS- FLAP BEAM 2 - INSPECTION OF FLAP BEAM BASE AND SIDE MEMBERS. **CONF ALL MODIFICATIONS None REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES Calculations, confirmed by fatigue and fail safe testing, show that on flap beam 2, transverse cracking may occur at the bolt holes of the flap beam base members and light alloy side members. During fatigue testing, the flap beam 2 developed cracks at the steel base member and light alloy side members lower flanges at approximately 43,000 simulated flights and failure occurred at approximately 48,000 simulated flights. For aircraft with an average flight time (AFT) greater than or equal to 1.5 hours Service Bulletin No. A300-57-6005 requires the flap beam 2 to be inspected upon completion of 15,000 Flight Cycles (FC). Repeat inspections are required at intervals of 1,500 flights as long as cracks are not found. Modification No. 05815H00968 (Service Bulletin No. A300-57-6006) introduces oversized interference fit bolts in cold expanded holes in order to increase the fatigue life of the flap beam base and side members. If no cracks are found, it is recommended that the modification should be embodied at the following aircraft lives: For aircraft with an AFT greater than or equal to 1.5 hours: - 15,000 FC / 32,400 FH (whichever occurs first). For aircraft with an AFT less than 1.5 hours: - 16,200 FC / 24,300 FH (whichever occurs first). The objective of this Service Bulletin requires the flap beam 2 to be inspected using ultrasonic techniques to detect cracks that extend from the bolt holes in the steel base member and aluminium side members. DATE: Aug 18/86 SERVICE BULLETIN No.: A300-57-6005 REVISION No.: 06 - Nov 14/13 Page: 1 7

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# @A300-600 SERVICE BULLETIN SUMMARY This Service Bulletin can detect signs of cracks at a sufficiently early stage of life to prevent the need to do expensive and time consuming repairs. GENERAL EVALUATION EVALUATION TABLE COMPLIANCE MANDATORY (1) CANCELS INSPECTION SB NO POTENTIAL AD YES A/C OPERATION AFFECTED NO RELIABILITY AFFECTED NO PAX COMFORT AFFECTED NO COST SAVING NO ETOPS AFFECTED NO STRUCTURAL LIFE EXTN NO VENDOR SB INVOLVED NO NOTE (1): Service Bulletin must be accomplished. MATERIAL PRICE INFORMATION No Material EFFECTIVITY This Service Bulletin is applicable to this (these) operator(s) :

ABD ABR BCS CES F2I FDX GBG I2L IRA IRM KAC KAL MGC MNB MON MSR MXU OHY QTR SUD TAR THA URS UZB CONCURRENT REQUIREMENTS None REFERENCES / REPERCUSSIONS TFU None OEB None AOT None SIL None LINE MAINTENANCE AFFECTED No LIFE LIMIT None OTHER None NATURE OF THE WORK AIRCRAFT YES EQUIPMENT NO HARD NO SOFT NO OBRM NO MANPOWER Task 576005-832-895-001: INSPECTION TOTAL MANHOURS 6.00 ELAPSED TIME (HOURS) 5.00 DATE: Aug 18/86 SERVICE BULLETIN No.: A300-57-6005 REVISION No.: 06 - Nov 14/13 Page: 2 7

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# @A300-600 SERVICE BULLETIN SUMMARY APPENDICES None

DATE: Aug 18/86 SERVICE BULLETIN No.: A300-57-6005 REVISION No.: 06 - Nov 14/13 Page: 3 7

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# @A300-600 SERVICE BULLETIN SUMMARY

**CONF ALL

D_SB_576005_7_SAAA_01_00 

### A Z532 (Z632)



## A

AREA OF INSPECTION **NOTE:** LH SHOWN RH SIMILAR

Figure A-USAAA - Sheet 01
DATE: Aug 18/86 SERVICE BULLETIN No.: A300-57-6005 REVISION No.: 06 - Nov 14/13 Page: 4 7

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# @A300-600 SERVICE BULLETIN
AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F Fax : (33) 5 61 93 42 51



# MANDATORYMANDATORYMANDATORY
ATA SYSTEM: 57 

### TITLE: WINGS- FLAP BEAM 2 - INSPECTION OF FLAP BEAM BASE AND SIDE MEMBERS. MODIFICATION No.: None This document contains AIRBUS PROPRIETARY INFORMATION and shall at all times remain the property of AIRBUS; no intellectual property right or licence is granted by AIRBUS in connection with any information contained in it. It is delivered on the express condition that said document and the information contained in it shall be treated as confidential, shall not be used for any purpose other than that for which it is hereby delivered. It shall not be disclosed in whole or in part to third parties and shall not be duplicated in any manner (except for the purposes of performing the tasks described hereunder and provided that any recipient of such document shall comply with the conditions herein), without AIRBUS prior written consent. 1. PLANNING INFORMATION **CONF ALL A. EFFECTIVITY NOTE: This Service Bulletin is applicable to all A300-600 aircraft, all certified models and all MSNs, except: - A300F4-622R aircraft on which the following AIRBUS modifications (Mod.) have been embodied: 11133H5409, 12047S21726, 12048S21727 and 12050S21744. - A300F4-650R and A300F4-622R aircraft on which both AIRBUS Mod. Nos. 11133H5409 and 12699S22372 have been embodied. (1) Models B4-603 B4-605R B4-620 B4-622 B4-622R C4-605R/F C4-620 F4-605R (2) Effectivity by MSN 0294 0344 0358 0361 0365 0380 0388 0401 0405 0408 0411 0414 0417 0464 0477 0479 0505 0518 0521 0525 0529-0530 0532 0536 0543 0546 0553-0561 0563 0572 0575 0577 0579 0581 0584 0602-0605 0607-0608 0611 0613-0614 0617-0618 0621 0623 0625-0626 0629-0633 0637 0641 0643 0657 0659 0662 0664 0666 0668 0670 0673 0677 0679 0681 0683 0688 0694 0696 0699 0701 0703 0705 0707 0709 0711 DATE: Aug 18/86 SERVICE BULLETIN No.: A300-57-6005 REVISION No.: 06 - Nov 14/13 Page: 1 7

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# @A300-600 SERVICE BULLETIN
0713 0715 0717 0719 0721-0730 0732-0746 0748-0750 0752-0764 0766-0775 0777-0794 0797 0799-0804 0836-0838 (3) Effectivity by Operator The Operator/MSN relationship is provided for information only and is correct at the time of issue in accordance with the information available to AIRBUS. Any future changes resulting from transfer of an aircraft from one operator to another will not be reflected in this list unless the Service Bulletin is revised for another reason. OPERATOR MSN ABD 0529 0557 ABR 0683 0770 BCS 0602 0617 0621 0637 0641 0670 0679 0703 0711 0724 0729 0730 0737 0740 0753 0783 CES 0532 0707 0725 0732 0741 0746 0754 0763 F2I 0294 0518 FDX 0358 0361 0365 0388 0417 0477 0479 0530 0536 0543 0555 0559 0572 0575 0579 0581 0611 0613 0625 0630 0633 0657 0659 0664 0668 0688 0709 0713 0715 0726 0728 0735 0736 0738 0742 0745 0748 0752 0757 0759 0760 0761 0766 0768 0769 0771 0772 0774 0777 0778 0779 0780 0781 0789 0790 0791 0792 0793 0794 0799 0800 0801 0802 0803 0804 GBG 0626 0643 I2L 0677 IRA 0632 0696 0723 0727 IRM 0380 0401 0405 0408 0411 0414 0546 0553 0608 0618 0623 0701 0750 0762 0773 0838 KAC 0344 0673 0694 0699 0719 0721 KAL 0631 0662 MGC 0743 MNB 0521 0525 0734 0739 0755 0756 0758 MON 0556 0604 0605 MSR 0561 0607 MXU 0767 0788 0797 0836 0837 OHY 0584 0603 0744 0749 0764 QTR 0554 0560 0614 SUD 0666 0775 TAR 0505 0558 0563 THA 0464 0577 0629 0681 0705 0782 0784 0785 0786 0787 URS 0733 UZB 0717 0722

DATE: Aug 18/86 SERVICE BULLETIN No.: A300-57-6005 REVISION No.: 06 - Nov 14/13 Page: 2 7

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# @A300-600 SERVICE BULLETIN (4) Configuration by MSN MSN CONFIGURATION 0294 0344 0358 0361 0365 0380 0388 0401 0405 0408 0411 0414 0417 0464 0477 0479 0505 0518 0521 0525 0529 0530 0532 0536 0543 0546 0553 0554 0555 0556 0557 0558 0559 0560 0561 0563 0572 0575 0577 0579 0581 0584 0602 0603 0604 0605 0607 0608 0611 0613 0614 0617 0618 0621 0623 0625 0626 0629 0630 0631 0632 0633 0637 0641 0643 0657 0659 0662 0664 0666 0668 0670 0673 0677 0679 0681 0683 0688 0694 0696 0699 0701 0703 0705 0707 0709 0711 0713 0715 0717 0719 0721 0722 0723 0724 0725 0726 0727 0728 0729 0730 0732 0733 0734 0735 0736 0737 0738 0739 0740 0741 0742 0743 0744 0745 0746 0748 0749 0750 0752 0753 0754 0755 0756 0757 0758 0759 0760 0761 0762 0763 0764 0766 0767 0768 0769 0770 0771 0772 0773 0774 0775 0777 0778 0779 0780 0781 0782 0783 0784 0785 0786 0787 0788 0789 0790 0791 0792 0793 0794 0797 0799 0800 0801 0802 0803 0804 0836 0837 0838 001

(5) Configuration definition **CONF 001 Config. 001 is valid for all the aircraft given in the effectivity of this Service Bulletin as a standard configuration. (6) Material Effectivity B. CONCURRENT REQUIREMENTS None C. REASON (1) History Calculations, confirmed by fatigue and fail safe testing, show that on flap beam 2, transverse cracking may occur at the bolt holes of the flap beam base members and light alloy side members. During fatigue testing, the flap beam 2 developed cracks at the steel base member and light alloy side members lower flanges at approximately 43,000 simulated flights and failure occurred at approximately 48,000 simulated flights. For aircraft with an average flight time (AFT) greater than or equal to 1.5 hours Service Bulletin No. A300-57-6005 requires the flap beam 2 to be inspected upon completion of 15,000 Flight Cycles (FC). Repeat inspections are required at intervals of 1,500 flights as long as cracks are not found. Modification No. 05815H00968 (Service Bulletin No. A300-57-6006) introduces oversized interference fit bolts in cold expanded holes in order to increase the fatigue life of the flap beam base and side members. If no cracks are found, it is recommended that the modification should be embodied at the following aircraft lives: DATE: Aug 18/86 SERVICE BULLETIN No.: A300-57-6005 REVISION No.: 06 - Nov 14/13 Page: 3 7

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# @A300-600 SERVICE BULLETIN For aircraft with an AFT greater than or equal to 1.5 hours: - 15,000 FC / 32,400 FH (whichever occurs first). For aircraft with an AFT less than 1.5 hours: - 16,200 FC / 24,300 FH (whichever occurs first). (2) Objective/Action The objective of this Service Bulletin requires the flap beam 2 to be inspected using ultrasonic techniques to detect cracks that extend from the bolt holes in the steel base member and aluminium side members. (3) Advantages This Service Bulletin can detect signs of cracks at a sufficiently early stage of life to prevent the need to do expensive and time consuming repairs. (4) Operational/Maintenance Consequences None D. DESCRIPTION To accomplish this Service Bulletin it is necessary to : Task 576005-832-895-001: INSPECTION (1) ULTRASONIC INSPECTION OF THE STEEL BASE MEMBER AND ALUMINIUM SIDE MEMBER ON FLAP BEAMS 2 (LH/RH) E. COMPLIANCE (1) Classification MANDATORY: Service Bulletin must be accomplished. (2) Accomplishment Timescale This Service Bulletin has been classified Mandatory. It is expected that an Airworthiness Directive (AD) published by the European Aviation Safety Agency (EASA) will be issued to confirm this classification. It is anticipated that the AD will confirm the (thresholds and/or intervals and/or date) given above but reference should be made to the AD for confirmation of the mandated accomplishment timescale.

DATE: Aug 18/86 SERVICE BULLETIN No.: A300-57-6005 REVISION No.: 06 - Nov 14/13 Page: 4 7

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# @A300-600 SERVICE BULLETIN

CONDITION CONFIGURATION INSPECTION THRESHOLD INSPECTION INTERVAL GRACE PERIOD Pre-Modification05815H00968 or PreModification 11133H05409 15,000 FC / 32,400 FH
Post Modification05815H00968 or PreModification 11133H05409 and bolts less than 11.11 mm (0.438 in) diameter **33,000 FC / 71,200 FH

Post Modification05815H00968 or PreModification 11133H05409 and bolts not less than 11.11 mm (0.438 in) diameter **22,000 FC / 47,500 FH For aircraft with

an average flight time (AFT) equal to or more than 1.5 hours

Post Modification 11133H05409 33,000 FC / 71,200 FH 1,500 FC / 3,200 FH 300 FC / 640 FH

Crack found Contact Airbus Before next flight Table 1: For aircraft with an average flight time (AFT) equal to or more than 1.5 hours
**NOTE: FC / FH from modification embodiment. CONDITION CONFIGURATION INSPECTION THRESHOLD INSPECTION INTERVAL GRACE PERIOD Pre-Modification05815H00968 or PreModification 11133H05409 16,200 FC / 24,300 FH
Post Modification05815H00968 or PreModification 11133H05409 and bolts less than 11.11 mm (0.438 in) diameter **35,600 FC / 53,400 FH

Post Modification05815H00968 or PreModification 11133H05409 and bolts not less than 11.11 mm (0.438 in) diameter **23,700 FC / 35,600 FH For aircraft with

an average flight time (AFT)

less than 1.5 hours

Post Modification 11133H05409 35,600 FC / 53,400 FH 1,600 FC /2,400 FH 300 FC / 640 FH

Crack found Contact Airbus Before next flight Table 2: For aircraft with an average flight time (AFT) less than 1.5 hours

DATE: Aug 18/86 SERVICE BULLETIN No.: A300-57-6005 REVISION No.: 06 - Nov 14/13 Page: 5 7

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# @A300-600 SERVICE BULLETIN
**NOTE: FC / FH from modification embodiment. F. APPROVAL The technical content of this document is approved under the authority of Design Organization Approval No. EASA.21J.031. If an aircraft listed in the effectivity has a modification or repair embodied that is not of AIRBUS origin, and which affects the content of this Service Bulletin, the operator is responsible for obtaining approval by its airworthiness authority for any adaptation necessary before incorporation of the Service Bulletin. G. MANPOWER The manpower estimates given in this Service Bulletin are based on the direct labor cost to do the work. These estimates assume that the work will be done by experienced personnel, and may need to be revised upwards to suit operator’s circumstances. The estimates do not include the time to prepare, plan or inspect the work. Manufacture and procurement of parts and tools, drying times for paints, sealants, etc., and general administration work are also not included. Task 576005-832-895-001: INSPECTION Get Access 2.00 On Aircraft ULTRASONIC INSPECTION OF THE STEEL BASE MEMBER AND ALUMINIUM SIDE MEMBER ON FLAP BEAMS 2 (LH/RH) 2.00 Close-Up 2.00 TOTAL MANHOURS 6.00 ELAPSED TIME (HOURS) 5.00 H. WEIGHT AND BALANCE Not Changed I. ELECTRICAL LOAD DATA Not Changed J. REFERENCES

Aircraft Maintenance Manual (AMM) 06-21-00 06-41-00 20-16-00 24-00-00 27-50-00 27-50-21 57-20-35 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-55-00 Non Destructive Test Manual (NTM) 57-20-11 K. PUBLICATION AFFECTED None
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# @A300-600 SERVICE BULLETIN
L. INTERCHANGEABILITY/MIXABILITY Not Applicable M. SPARES None

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# @A300-600 SERVICE BULLETIN

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# @A300-600 SERVICE BULLETIN
2. MATERIAL INFORMATION **CONF ALL A. MATERIAL - PRICE AND AVAILABILITY (1) Procurement Addresses None (2) Price and Availability None B. INDUSTRY SUPPORT INFORMATION None C. LIST OF COMPONENTS No Kit D. LIST OF MATERIALS - OPERATOR SUPPLIED None E. PARTS TO BE RE-IDENTIFIED BY OPERATOR None F. TOOLING None

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# @A300-600 SERVICE BULLETIN

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# @A300-600 SERVICE BULLETIN
3. ACCOMPLISHMENT INSTRUCTIONS Task 576005-832-895-001 - INSPECTION WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. WARNING: MAKE SURE THAT THE SAFETY DEVICES AND THE WARNING NOTICES ARE IN POSITION BEFORE YOU START A TASK ON OR NEAR: - THE FLIGHT CONTROLS - THE FLIGHT CONTROL SURFACES - THE LANDING GEAR AND THE RELATED DOORS - COMPONENTS THAT MOVE. MOVEMENT OF COMPONENTS CAN KILL OR INJURE PERSONS. CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING, COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO THIS: - PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC. AS NECESSARY ON WIRING AND COMPONENTS - REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND OTHER CONTAMINATION. THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION. IF THERE IS CONTAMINATION, REFER TO ESPM 20-55-00. NOTE: The accomplishment instructions of this Service Bulletin refer to procedures included in other AIRBUS documents. When the words ’refer to’ are used and the operator has an accepted alternative procedure, the accepted alternative procedure can be used. When the words ’in accordance with’ are included in the instruction, the procedure in the AIRBUS document must be used. NOTE: The access and close-up instructions, not comprising return to service tests, in this Service Bulletin do not constitute or affect the technical intent of the Service Bulletin. Operators can therefore, as deemed necessary, omit or add access and/or close-up steps to add flexibility to their maintenance operations as long as the technical intent of the Service Bulletin is met within the set parameters. NOTE: Manual titles given in the accomplishment instructions are referred to by acronyms. Refer to paragraph 1.J., References, for the definition of acronyms. NOTE: This Service Bulletin is classified mandatory or expected to be classified mandatory

DATE: Aug 18/86 SERVICE BULLETIN No.: A300-57-6005 REVISION No.: 06 - Nov 14/13 Page: 11 7

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# @A300-600 SERVICE BULLETIN by an Airworthiness Directive (AD). The paragraphs 3.C. and 3.D. in these accomplishment instructions are Required for Compliance (RC) and must be done to comply with the AD. Other paragraphs are recommended and may be deviated from, done as part of other actions or done with accepted methods different from those given in the Service Bulletin, as long as the RC paragraphs can be done and the aircraft can be put back into a serviceable condition. NOTE: The purpose of flow charts is to supplement the information given in the Procedure and Compliance paragraphs and not to serve as the primary source for tasks or compliance times given in this Service Bulletin. Task Associated Data Zone 532 632 Access Door 575FB 675FB AL AR Panel AL AR Manpower TOTAL MANHOURS 6.00 ELAPSED TIME (HOURS) 5.00 A. GENERAL (1) Subtask 576005-910-401-001 - STANDARD PRACTICES Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001 06-41-00, Page Block 001 20-16-00, Page Block 201 Consumable Material List (CML) Non Destructive Test Manual (NTM) 57-20-11 (a) For the specification of materials (Mat. No.) given in this Service Bulletin refer to the Consumable Materials List (CML). (b) For the identification of zones, refer to AMM 06-21-00, Page Block 001. (c) For the identification of access panels, refer to AMM 06-41-00, Page Block 001. (d) For the circuit breaker safety precautions, refer to AMM 20-16-00, Page Block 201. (e) For ultrasonic evaluation of crack lengths (Refer to NTM 57-20-11). (2) Subtask 576005-839-401-001 - ADMINISTRATIVE Manpower Resources Skills NON SPECIFIC DATE: Aug 18/86 SERVICE BULLETIN No.: A300-57-6005 REVISION No.: 06 - Nov 14/13 Page: 12 7

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# @A300-600 SERVICE BULLETIN Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. B. PREPARATION (1) Subtask 576005-941-401-001 - GET ACCESS TO THE FLAP BEAMS Work Zones and Access Panels Zone Access/Work location 532 Access Door 575FB, Door AL Work location Panel 133VU 632 Access Door 675FB Panel AR Work location Panel 133VU Manpower Resources Skills AIRFRAME References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 27-50-00, Page Block 301 27-50-21, Page Block 401 57-20-35, Page Block 401 Consumable Material List (CML) (a) Make sure that the aircraft is electrically grounded (Refer to AMM 24-00-00, Page Block 301). (b) Remove the fixed fairings from flap beam 2 (Refer to AMM 57-20-35, Page Block 401). (c) Fully extend the flap (Refer to AMM 27-50-00, Page Block 301). (d) Remove the moveable fairings from flap beam 2 (Refer to AMM 27-50-21, Page Block 401). (e) Put the access platform(s) in position below the flap beam 2. C. PROCEDURE (1) Subtask 576005-832-401-001 - ULTRASONIC INSPECTION OF THE STEEL BASE MEMBER AND ALUMINIUM SIDE MEMBER ON FLAP BEAMS 2 (LH/RH) Work Zones and Access Panels Zone Access/Work location 532 Access Door 575FB Panel AL Work location Panel 133VU 632 Access Door 675FB Panel AR Work location Panel 133VU DATE: Aug 18/86 SERVICE BULLETIN No.: A300-57-6005 REVISION No.: 06 - Nov 14/13 Page: 13 7

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# @A300-600 SERVICE BULLETIN
Manpower Resources Manhours 2.00 Minimum number of person 1 Subtask elapsed time 2.00 Skills AIRFRAME References Non Destructive Test Manual (NTM) 57-20-11 Part 4, Procedure A 57-20-11 Part 4, Procedure B Fig. A-UBAAA FLAP TRACK 2 SIDE MEMBER ASSEMBLY Sheet 01 Fig. A-UCAAA FLAP TRACK 2 BASE MEMBER ASSEMBLY Sheet 01 Fig. A-UDAAA FLAP TRACK 2 SIDE MEMBER ASSEMBLY AREA OF INSPECTION Sheet 01 Fig. A-UEAAA SECTION THROUGH FLAP BEAM 2 ASSEMBLY Sheet 01 Fig. A-UFAAA FLOWCHART Sheet 01
Refer to Fig. A-UFAAA Sheet 01 for the ultrasonic inspection procedure. (a) Do an ultrasonic inspection of the steel base member of the flap beam 2 for cracks that extend from the bolt holes (Refer to NTM 57-20-11 Part 4, Procedure A, Fig. A-UBAAA Sheet 01 , Fig. A-UCAAA Sheet 01 , Fig. A-UDAAA Sheet 01 and Fig. AUEAAA Sheet 01 ). (b) Do an ultrasonic inspection of the aluminium side members of the flap beam 2 for cracks that extend from the bolt holes (Refer to NTM 57-20-11 Part 4, Procedure B, Fig. A-UBAAA Sheet 01 , Fig. A-UCAAA Sheet 01 , Fig. A-UDAAA Sheet 01 and Fig. A-UEAAA Sheet 01 ). (c) If cracks are found in either of the side members or the base member that are to the edge, or extend as much as 4.0 mm (0.157 in.) beyond the bolt hole, a repeat inspection must be done every 250 FC. (d) If cracks are found in either of the side members or the base member that are more than 4.0 mm (0.157 in.) beyond the bolt hole, the flap beam must be replaced before the next flight. (e) If no cracks are found, refer to SUBTASK 576005-942-401 001 CLOSE-UP . (f) All inspection results, including nil findings, should be sent to AIRBUS with a copy of Fig. A-UCAAA Sheet 01 as a reporting form.

DATE: Aug 18/86 SERVICE BULLETIN No.: A300-57-6005 REVISION No.: 06 - Nov 14/13 Page: 14 7

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# @A300-600 SERVICE BULLETIN
D. TEST None E. CLOSE-UP (1) Subtask 576005-942-401-001 - CLOSE-UP Work Zones and Access Panels Zone Access/Work location 532 Access Door 575FB, Door AL Work location Panel 133VU 632 Access Door 675FB, Door AR Work location Panel 133VU Manpower Resources Skills AIRFRAME References Aircraft Maintenance Manual (AMM) 27-50-00, Page Block 301 27-50-21, Page Block 401 57-20-35, Page Block 401 (a) Install the moveable fairings on flap beam 2 (Refer to AMM 27-50-21, Page Block 401). (b) Fully retract the flaps (Refer to AMM 27-50-00, Page Block 301). (c) Install the fixed fairings on flap beam 2 (Refer to AMM 57-20-35, Page Block 401). (d) Restore the systems and the aircraft to the normal operating conditions. (e) Report all findings, including nil finding to AIRBUS on the form provided in this Service Bulletin. (f) Remove the access platforms from flap beam 2 area. (g) Make sure that the work areas are clean and clear of tools and other items of equipment.

DATE: Aug 18/86 SERVICE BULLETIN No.: A300-57-6005 REVISION No.: 06 - Nov 14/13 Page: 15 7

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# @A300-600 SERVICE BULLETIN

**CONF ALL

AREA OF INSPECTION AREA OF INSPECTION FOR DETAILS SEE A−UCAAA

D_SB_576005_7_BAAA_01_00 

### A Z532 (Z632)

**FWD** C/L DUPLEX

DRIVE LH SHOWN RH SIMILAR



## A **A**

**A** AREA OF INSPECTION FOR DETAILS SEE A−UCAAA



## A **A**

Figure A-UBAAA - Sheet 01 FLAP TRACK 2 SIDE MEMBER ASSEMBLY DATE: Aug 18/86 SERVICE BULLETIN No.: A300-57-6005 REVISION No.: 06 - Nov 14/13 Page: 16 7

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# @A300-600 SERVICE BULLETIN

**CONF ALL



### A Z532 (Z632)



## A **B** LH SHOWN RH SIMILAR

TYPICAL CRACK PROPOGATION DIRECTION OF

**F W**  **D** VIEW ON UNDERSIDE OF FLAP BEAM 2 ASSEMBLY **NOTE:** RECORD THE CRACK POSITIONS AND LENGTHS 01 01

IN BASE MEMBERS ON THIS FIGURE AND RETURN THE INFORMATION BACK TO AIRBUS. D_SB_576005_7_CAAA_01_00 

### B

**B**

Figure A-UCAAA - Sheet 01 FLAP TRACK 2 BASE MEMBER ASSEMBLY DATE: Aug 18/86 SERVICE BULLETIN No.: A300-57-6005 REVISION No.: 06 - Nov 14/13 Page: 17 7

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# @A300-600 SERVICE BULLETIN

**CONF ALL



### B

TYPICAL CRACK PROPOGATION 

### A Z532 (Z632)



## A

**B**

D_SB_576005_7_DAAA_01_00 LH SHOWN RH SIMILAR

DIRECTION OF

Figure A-UDAAA - Sheet 01 FLAP TRACK 2 SIDE MEMBER ASSEMBLY AREA OF INSPECTION DATE: Aug 18/86 SERVICE BULLETIN No.: A300-57-6005 REVISION No.: 06 - Nov 14/13 Page: 18 7

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# @A300-600 SERVICE BULLETIN

**CONF ALL

LIGHT ALLOY SIDE MEMBER

STEEL STRAPS STEEL STRAPS

STEEL BASE MEMBER

SECTION THROUGH FLAP BEAM 2 ASSEMBLY THE LOWER HALF OF THE FLAP BEAM STRUCTURE CONSTITUTES A TENSION BOOM ASSEMBLY MADE FROM THE FOLLOWING ELEMENTS: TWO LIGHT ALLOY SIDE MEMBERS, A STEEL BASE MEMBER AND FOUR STEEL STRAPS, TWO EACH SIDE AS ILLUSTRATED ABOVE. WHEN CRACKS ARE FOUND THE FOLLOWING LIMITATIONS APPLY: DESCRIPTION REPEAT INSPECTIONS A CRACK IN EITHER SIDE MEMBER OR BASE MEMBER TO EDGE OR UP TO 4.000 mm (0.157 in) BEYOND BOLT HOLE. CRACK IN EITHER SIDE MEMBER OR BASE MEMBER GREATER THAN 4.000 mm (0.157 in) BEYOND BOLT HOLE. 250 FLIGHTS

REPLACE IMMEDIATELY 1.

2. LIGHT ALLOY SIDE MEMBER

D_SB_576005_7_EAAA_01_00 Figure A-UEAAA - Sheet 01 SECTION THROUGH FLAP BEAM 2 ASSEMBLY DATE: Aug 18/86 SERVICE BULLETIN No.: A300-57-6005 REVISION No.: 06 - Nov 14/13 Page: 19 7

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# @A300-600 SERVICE BULLETIN

**CONF ALL

QUESTION ACTION FINDING NO YES

COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN. AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR **NOTE:** THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE REPEAT INSPECTIONS AT INTERVALS IN ACCORDANCE

D_SB_576005_7_FAAA_01_00 ULTRASONIC INSPECTION OF THE STEEL BASE MEMBER

OF THE FLAP BEAM 2 FOR CRACKS EXTENDING FROM THE BOLT HOLES AND ULTRASONIC INSPECTION OF THE ALUMINUM SIDE MEMBERS OF THE FLAP BEAM 2. THRESHOLD IN ACCORDANCE WITH PARAGRAPH 1.E(2)

ARE THERE ANY

CRACKS?

WITH PARAGRAPH 1.E(2) THE LENGTH LESS THAN 4.000 mm NO YES

REPEAT INSPECTIONS

EVERY 250 FLIGHT CYCLES REPLACE FLAP BEAM BEFORE NEXT FLIGHT

REPEAT INSPECTIONS AT INTERVALS IN ACCORDANCE

WITH PARAGRAPH 1.E(2) IS (0.157 in) ?

Figure A-UFAAA - Sheet 01 FLOWCHART DATE: Aug 18/86 SERVICE BULLETIN No.: A300-57-6005 REVISION No.: 06 - Nov 14/13 Page: 20 7

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# @A300-600 SERVICE BULLETIN REPORTING SHEET 

### TITLE: WINGS- FLAP BEAM 2 - INSPECTION OF FLAP BEAM BASE AND SIDE MEMBERS. MODIFICATION No.: None Please complete the appropriate item (A or B): A - SB WILL BE embodied YES/NO (if NO please comment) If YES, aircraft concerned (as per SB effectivity by default) and planned dates (month/year) of embodiment:

B - SB HAS BEEN embodied on aircraft: Operator comments:
From Airline: Name/Title: Signature: Date: If operational documentation is affected (see Paragraph 1.K of this SB): If information is needed prior to next normal revision or prior to SB embodiment, please indicate required service(s): Either: Modification Operational Impact (MOI), if available YES/NO Or : Intermediate revision YES/NO Important Information: This SB will only be incorporated in your maintenance and operational documentation if this sheet is returned to Airbus and signed by a duly authorised representative. With the next feasible revision, this will result in - Updating of maintenance documentation to show pre and post SB data. - Updating of maintenance and operational documentation to show post SB data after embodiment. If this SB requires previous or simultaneous accomplishment of other SBs, Airbus shall automatically include them in the manual revisions. Refer to SIL 00-037 for detailed information. Please return this completed sheet to: AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Attn: SDC32 Technical Data and Documentation Services FAX: (+33) 5 61 93 28 06 e-mail: sb.reporting@airbus.com or via your Resident Customer Support Office. Alternatively, SB lists via letters or fax are also accepted.

DATE: Aug 18/86 SERVICE BULLETIN No.: A300-57-6005 REVISION No.: 06 - Nov 14/13 Page: 1 7

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# @A300-600 SERVICE BULLETIN QUALITY PERCEPTION FORM Use this form to tell us what is your perception of the quality of this Service Bulletin. The reported data that you provide us will be used to analyse areas of difficulties and to take corrective action to further improve the quality of our Service Bulletins. We thank you for the time you have taken in completing this form. (Please rate on a scale of 1 to 4, with 4 being the highest score) - Quality rating of this SB 4321 - Quality rating of the Accomplishment Instructions 4321 - Quality rating of the Illustrations 4321 - Is this SB easy to understand ? Y/N If you have had difficulties in the accomplishment of this SB please quote below the area(s) and give a short description of the issue. Planning Material Instructions X Effectivity X Kit content X Preparation X Reason X List of Materials Operator Supplied X Mod/Inspection X Manpower X Industry support X Test X References X Re-identification X Close-Up X Publication X Tooling X Illustrations Comments:

Operator: Date: Name/Title: Please return this form to: AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Attn : SEM4 Service Bulletins Management FAX : (33) 5 61 93 42 51 Or via your Resident Customer Support Office.

DATE: Aug 18/86 SERVICE BULLETIN No.: A300-57-6005 REVISION No.: 06 - Nov 14/13 Page: 1 7

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